An Affordable, Hybrid-Electric Propulsion Architecture for Small Transfer Stages

QAM is pleased to present this proposal to demonstrate feasibility of an affordable O2/CH4 propulsion system architecture that is well suited for a small transfer stage that enables reliable ride share opportunities for cubesat development teams around the world. The uncomplicated multi-start architecture derives its affordability through a reliance upon the use of proven thruster technology and alternative fuel technology borrowed from the automotive industry. Namely, it uses a hybrid electric power cycle for both motive and electrical power, as well as low pressure (~500 psi) gas adsorption propellant tanks. As a result, the proposed architecturemdash;called ldquo;HERArdquo; (hybrid electric rocket assembly)mdash;boasts high performance, (at least 340-sec delivered vacuum Isp) and much better propellant fraction than scaling laws predict (generally speaking, stage dry mass and achievable propellant fraction are directly proportional).